CN105555660A - Self-aligning fitting assemblies and systems and methods including the same - Google Patents
Self-aligning fitting assemblies and systems and methods including the same Download PDFInfo
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- CN105555660A CN105555660A CN201480051396.0A CN201480051396A CN105555660A CN 105555660 A CN105555660 A CN 105555660A CN 201480051396 A CN201480051396 A CN 201480051396A CN 105555660 A CN105555660 A CN 105555660A
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- attachment hole
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- 238000000034 method Methods 0.000 title claims abstract description 68
- 230000000712 assembly Effects 0.000 title abstract 4
- 238000000429 assembly Methods 0.000 title abstract 4
- 238000013519 translation Methods 0.000 claims description 46
- 238000010276 construction Methods 0.000 claims description 7
- 230000001815 facial effect Effects 0.000 claims description 5
- 230000033001 locomotion Effects 0.000 claims description 5
- 230000008859 change Effects 0.000 claims description 3
- 238000010586 diagram Methods 0.000 description 10
- 238000009434 installation Methods 0.000 description 8
- 238000004519 manufacturing process Methods 0.000 description 6
- 230000009467 reduction Effects 0.000 description 5
- 230000006978 adaptation Effects 0.000 description 3
- 238000013461 design Methods 0.000 description 3
- 230000009471 action Effects 0.000 description 2
- 230000003044 adaptive effect Effects 0.000 description 2
- 238000006243 chemical reaction Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 239000000654 additive Substances 0.000 description 1
- 230000000996 additive effect Effects 0.000 description 1
- 230000008602 contraction Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
- 230000008961 swelling Effects 0.000 description 1
- 238000012360 testing method Methods 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/18—Floors
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/068—Fuselage sections
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/10—Manufacturing or assembling aircraft, e.g. jigs therefor
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T29/00—Metal working
- Y10T29/49—Method of mechanical manufacture
- Y10T29/49826—Assembling or joining
- Y10T29/49895—Associating parts by use of aligning means [e.g., use of a drift pin or a "fixture"]
- Y10T29/49902—Associating parts by use of aligning means [e.g., use of a drift pin or a "fixture"] by manipulating aligning means
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Connection Of Plates (AREA)
- Automatic Assembly (AREA)
- Body Structure For Vehicles (AREA)
- Floor Finish (AREA)
Abstract
Self-aligning fitting assemblies (100) and systems and methods including the same are disclosed herein. The self-aligning fitting assemblies include a barrel-side fitting (160) that includes a plurality of barrel-side attachment holes (162) and a floor-side fitting (180) that includes a plurality of floor-side attachment holes (182). The self-aligning fitting assemblies also include an alignment pin recess (120) and a fitting alignment recess (110). The methods include translating a floor grid (80) relative to a fuselage barrel (60), operatively aligning a plurality of alignment pin recesses (120) with a corresponding plurality of fitting alignment recesses (110), and locating a plurality of alignment pins (130) within the plurality of alignment pin recesses such that each of the plurality of alignment pins extends through a respective one of the plurality of fitting alignment recesses. The methods also include lowering the floor grid (80) relative to the fuselage barrel (60) and installing a plurality of fasteners.
Description
Technical field
The disclosure relates in general to autoregistration load module, and more specifically, relates to the autoregistration load module that may be used for the floor grid of body to aim at the fuselage cylinder of body, and/or relate to the system and method utilizing autoregistration load module.
Background technology
Aircraft generally include manufacture separately and the sub-component of the multiple different or separation combined at the assembly process of aircraft subsequently.Each in these sub-components may be fabricated to the production tolerance with regulation in different place (geographically and/or in specific fabrication shop).Often, these sub-components may be very large, and upon carries out assembling the challenge that may have in unique manufacture in order to build aircraft.
Illustratively, non-exclusive example, the floor grid of aircraft or passangers floor grid can separate with the fuselage cylinder of aircraft or fuselage and manufacture.Subsequently, floor grid can be positioned in fuselage cylinder and to be operationally attached to fuselage cylinder.Floor grid and fuselage cylinder are all relative large parts, and their assembling can need special support and/or transport structure.In addition, floor grid and fuselage cylinder to being the consuming time and/or expensive process needing a large amount of manufacturing recourses.Therefore, exist for autoregistration load module and/or the needs for the system and/or method that comprise autoregistration load module.
Summary of the invention
Disclosed herein autoregistration load module and comprise the system and method for autoregistration load module.Autoregistration load module comprises the cylinder side assembly parts with multiple side attachment hole and the floor side assembly parts with multiple floor side attachment hole.Autoregistration load module also comprises alignment pin recess and assembly alignment recess.Alignment pin recess is formed in the one in a side assembly parts and floor side assembly parts, and assembly alignment recess is formed in the another one in a side assembly parts and floor side assembly parts.Alignment pin recess configuration becomes to receive the alignment pin comprising alignment surface.When alignment pin is received in alignment pin recess, alignment surface extends through assembly alignment recess.Assembly alignment recess size is formed as allowing alignment surface translation wherein.Therefore, assembly alignment recess allows cylinder side assembly parts and the relative to each other translation between first orientation and second orientation of floor side assembly parts, in first orientation, multiple floor side attachment hole is not aimed at multiple side attachment hole, and in second orientation, multiple floor side attachment hole is aimed at multiple side attachment hole.
Method comprises relative to fuselage cylinder translation floor grid, floor grid to be operatively positioned in fuselage cylinder.Floor grid is operatively attached to the multiple floor side assembly parts comprising multiple floor side attachment hole.Fuselage cylinder is operatively attached to the multiple side assembly parts comprising multiple side attachment hole.The method also comprises operatively aims at multiple alignment pin recess with corresponding multiple assembly alignment recesses.Multiple alignment pin recess is formed in the one in multiple floor side assembly parts and multiple side assembly parts.Multiple assembly alignment recess is formed in the another one in multiple floor side assembly parts and multiple side assembly parts.The method also comprises and is positioned in multiple alignment pin recess by multiple alignment pin, extends through a corresponding assembly alignment recess in multiple assembly alignment recess to make each alignment pin in multiple alignment pin.The method comprises relative to fuselage cylinder reduction floor grid further, to make multiple side assembly parts and multiple floor side assembly parts relative to each other move to second orientation from first orientation, in first orientation, multiple floor side attachment hole is not aimed at multiple side attachment hole, in second orientation, multiple floor side attachment hole is aimed at multiple side attachment hole.Multiple assembly alignment recess is configured as and guides multiple floor side assembly parts and multiple side assembly parts towards second orientation during the step reduced.The method also comprises by making each fastener in multiple fastener extend through a floor side attachment hole selected in multiple floor side attachment hole and install multiple fastener by a cylinder side attachment hole corresponding in multiple side attachment hole.
Accompanying drawing explanation
Fig. 1 is according to the schematic diagram of body that can comprise fuselage cylinder, floor grid and autoregistration load module of the present disclosure.
Fig. 2 is the schematic diagram of illustrative, the non-exclusive example according to body package system of the present disclosure, and this body package system may be used for building body at least partially.
Fig. 3 is the schematic diagram of illustrative, the non-exclusive example according to autoregistration load module of the present disclosure.
Fig. 4 is the exploded drawings of illustrative, the non-exclusive example according to autoregistration load module of the present disclosure.
Fig. 5 is the partial view according to autoregistration load module of the present disclosure under first orientation.
Fig. 6 is the partial view of the autoregistration load module of Fig. 5 under second orientation.
Fig. 7 is the diagram of circuit according to method of the present disclosure describing assembling body.
Detailed description of the invention
Fig. 1-7 provides according to autoregistration load module 100 of the present disclosure, body 50, body package system 20, its parts and/or the illustrative non-exclusive examples of method utilizing it, body can comprise autoregistration load module 100, and body package system can comprise and/or utilize autoregistration load module 100.For using identical labelled notation in element that is similar or at least object of basic simlarity each figure in figures 1-7, and these elements can not be discussed with reference to each figure in Fig. 1-7 in this article in detail.Similarly, all elements can not mark in each figure in figures 1-7, but in order to conformability, can use reference number associated therewith in this article.Element, parts and/or feature that one or more figure in reference Fig. 1-7 discuss in this article can comprise in figures 1-7 any one and/or use together with any one in these figure under the prerequisite not deviating from the scope of the present disclosure.
Usually, the element solid line be probably included in given (that is, concrete) embodiment illustrates, and is that optional element is shown in broken lines for given embodiment.But, be not be all necessary for all embodiments with the element shown in solid line, and when not deviating from the scope of the present disclosure, can save from detailed description of the invention with the element shown in solid line.
Fig. 1 is the schematic diagram according to body 50 of the present disclosure.Body 50 can form a part for body package system 20, can use together with body package system, and/or can build with body package system, and body can also form a part for aircraft 48.
Body 50 can comprise fuselage cylinder 60, floor grid 80 and according to multiple autoregistration load module 100 of the present disclosure.As here discussed in more detail, autoregistration load module 100 can be selected, designing, adaptive, structure, size form and/or be configured to and operationally make floor grid 80 aim at fuselage cylinder 60 during assembling body 50.In addition or alternatively, autoregistration load module 100 can also be selected, design, adaptive, structure, size form and/or be configured to and operationally floor grid 80 is attached to fuselage cylinder 60 during assembling body 50 and/or after assembling body.
Autoregistration load module 100 can comprise a side assembly parts 160, and these side assembly parts can operationally be attached to fuselage cylinder 60 before being positioned in fuselage cylinder 60 by floor grid 80.Autoregistration load module 100 can also comprise floor side assembly parts 180, and these floor side assembly parts can operationally be attached to floor grid 80 before being positioned in fuselage cylinder 60 by floor grid 80.After floor grid 80 is positioned in fuselage cylinder 60, cylinder side assembly parts 160 can operationally be attached to floor side assembly parts 180, operationally floor grid 80 is attached to fuselage cylinder 60.
Floor grid 80 can defining surface 82, and this surface also can be called passenger surface 82 in this article and/or be called upper surface 82.Surface 82 can limit (or can be called in this article) surface plane 82 and/or way bill facial plane 82.Surface plane 82 can defining surface normal direction (normaldirection) 84.
Fig. 2 is the schematic diagram that may be used for the illustrative non-exclusive example according to body package system 20 of the present disclosure at least partially building body 50.Body package system 20 can be configured to operationally floor grid 80 is attached to fuselage cylinder 60 with limiting body 50.
Body package system 20 can comprise floor grid translation structure 30, and this floor grid translation structure can be configured to operationally locate floor grid 80 relative to fuselage cylinder 60.Floor grid translation structure 30 can comprise and/or be gauntry crane 32, and this gauntry crane is configured to operationally translation floor grid 80.Floor grid translation structure 30 can also comprise and/or be floor grid support fixture 34, and this fixture structure becomes operationally support floor grid 80.
Body package system 20 can also comprise fuselage cylinder supporting construction 40.Fuselage cylinder supporting construction 40 can be configured to operationally support fuselage cylinder while floor grid 80 is operationally located relative to fuselage cylinder 60.
As here discussed in more detail, fuselage cylinder 60 can comprise one or more side assembly parts 160.In addition, floor grid 80 can comprise one or more floor side assembly parts 180.During assembling fuselage cylinder 60, cylinder side assembly parts 160 and floor side assembly parts 180 can form autoregistration load module 100.Autoregistration load module 100 can be configured to during assembling body 50 and/or after assembling body, floor grid 80 is aimed at fuselage cylinder 60 collaboratively and/or operationally floor grid 80 is attached to fuselage cylinder 60.
Fig. 3 is the schematic diagram of the illustrative non-exclusive example according to autoregistration load module 100 of the present disclosure.Autoregistration load module 100 can also be called load module 100 in this article and/or be called assembly 100.Assembly 100 be configured to by floor grid 80 and body 50 and/or the fuselage cylinder 60 of aircraft 48 aim at and be operationally attached.
Autoregistration load module 100 comprises a side assembly parts 160 and floor side assembly parts 180.Cylinder side assembly parts 160 are configured to such as operationally be attached to fuselage cylinder 60 via one or more side holding structures 164.In addition, floor side assembly parts 180 are configured to such as operationally be attached to floor grid 80 via one or more floor side holding structure 184.
Cylinder side assembly parts 160 comprise and/or limit multiple side attachment hole 162, and floor side assembly parts 180 comprise and/or limit multiple floor side attachment hole 182.Each design in multiple floor side attachment hole 182, adaptation, structure, size are formed and/or orientate as and operationally aim at, as shown in Figure 3 to corresponding in multiple side attachment hole 162.Exercisable like this aligning can allow expansion pin 140 and/or fastener 150 to insert wherein, as discussed in more detail here.
Autoregistration load module 100 also comprises and/or limits alignment pin recess 120.Alignment pin recess 120 is shown in broken lines to indicate alignment pin recess 120 to be limited by cylinder side assembly parts 160 and/or formed in the assembly parts of cylinder side or limited by floor side assembly parts 180 in figure 3.Alignment pin recess 120 size is formed as receiving alignment pin 130, and this alignment pin extends to limit alignment surface 132 from alignment pin recess 120.As shown in Figure 3, the internal dimensions of alignment pin recess 120 can at least with the outside dimension basic simlarity of alignment pin 130.Therefore, alignment pin 130 can be received in alignment pin recess 120 substantially motionless for alignment pin recess up to looking younger.
Autoregistration load module 100 also comprises and/or limits assembly alignment recess 110.Assembly alignment recess 110 is shown in broken lines to indicate assembly alignment recess 110 to be limited by cylinder side assembly parts 160 and/or formed in the assembly parts of cylinder side or limited by floor side assembly parts 180 in figure 3.Usually, alignment pin recess 120 will be limited by cylinder side assembly parts 160 or floor side assembly parts 180 and/or be formed in them one, and assembly alignment recess 110 will be limited by another in cylinder side assembly parts 160 and floor side assembly parts 180 and/or be formed in another in them.
Alignment pin 130 to be received in alignment pin recess 120 and autoregistration load module 100 for fuselage cylinder 60 being aligned to and/or being operationally attached to floor grid 80 time, alignment pin 130 and/or its alignment surface 132 can extend from alignment pin recess 120 and by assembly alignment recess 110.
As shown in Figure 3, assembly alignment recess 110 can size be formed as allowing alignment surface 132 translation wherein.Therefore, assembly alignment recess 110 can allow a side assembly parts 160 relative to floor side assembly parts 180 translation.Such translation can be included in following among translation, the plurality of relative azimuth comprises: at least the first relative azimuth, and wherein multiple floor side attachment hole 182 is not aimed at multiple side attachment hole 162; And second relative azimuth, wherein multiple floor side attachment hole 182 is aimed at multiple side attachment hole 162.To discuss in more detail with reference to Fig. 5-6 in this article this.
In the scope of the present disclosure, cylinder side assembly parts 160 can limit the cylinder side attachment hole 162 of any suitable quantity.Similarly, in the scope of the present disclosure, floor side assembly parts 180 also can limit the floor side attachment hole 182 of any suitable quantity.As illustrative non-exclusive example, cylinder side assembly parts 160 can limit at least 2, just in time 2, at least 3, just in time 3, at least 4 or just in time 4 cylinder side attachment hole 162; And floor side assembly parts 180 can limit the floor side attachment hole 182 of corresponding quantity.
Alignment pin recess 120 can comprise any suitable structure being configured to receive and/or keep alignment pin 130.As illustrative non-exclusive example, alignment pin recess 120 can comprise and/or be hole, cylindrical hole, size be formed as receiving the cylindrical hole with shallow embedding head bore that the cylindrical hole of threaded portion of alignment pin 130 and/or size are formed as receiving the threaded portion of alignment pin 130 and a part for alignment surface 132.In addition, alignment pin 130 can comprise any suitable structure that may be received in alignment pin recess 120 and/or comprise alignment surface 132.As illustrative non-exclusive example, alignment pin 130 can comprise and/or be pin, bolt and/or rotator bolt (shoulderbolt).
When there is expansion pin 140, this expansion pin can comprise following any suitable structure, namely this structure can be configured to extend through selected floor side attachment hole 182 and the cylinder side attachment hole 162 by correspondence, operationally selected floor side attachment hole 182 to be aimed at corresponding cylinder side attachment hole 162.As illustrative non-exclusive example, expansion pin 140 can be configured to comprise and/or limit contracted diameter retracted configuration and comprise and/or limit swell diameter expansion form between change, wherein swell diameter is greater than contracted diameter.
In operation, and as here discussed in more detail, selected floor side attachment hole 182 can such as via being positioned at by alignment pin 130 in alignment pin recess 120 and being positioned in assembly alignment recess 110 partly to aim at corresponding cylinder side attachment hole 162.Then expansion pin 140 can be positioned in selected floor side attachment hole 182 and corresponding both cylinder side attachment hole 162 while expansion pin 140 is in contraction state.Then, expansion pin 140 can convert swelling state to.Selected floor side attachment hole 182 can operationally be aimed at corresponding cylinder side attachment hole 162 by the conversion of expansion pin 140.Then fixing device can be utilized at least provisionally cylinder side assembly parts 160 and floor side assembly parts 180 to be fixed on the relative azimuth of expectation under.Then expansion pin 140 can be removed from selected floor side attachment hole 182 and from the cylinder side attachment hole 162 of correspondence, thus allows fastener 150 to be positioned in the selected interior cylinder side attachment hole 162 being also also positioned at correspondence of floor side attachment hole 182.Then fastener 150 can be tightened with under cylinder side assembly parts 160 and floor side assembly parts 180 are remained on the relative azimuth of expectation.Subsequently, fixing device can be removed.
Fig. 4 be according to autoregistration load module 100 of the present disclosure more specifically but still be the exploded drawings of illustrative non-exclusive example.The autoregistration load module 100 of Fig. 4 can comprise and/or be the autoregistration load module 100 of Fig. 1-3.
In the diagram, autoregistration load module 100 comprises a side assembly parts 160 and floor side assembly parts 180.Cylinder side assembly parts 160 comprise and/or limit multiple side attachment hole 162, and floor side assembly parts 180 comprise and/or limit multiple floor side attachment hole 182.Cylinder side assembly parts 160 also comprise and/or limit cylinder side holding structure 164, and this side holding structure is configured to operationally cylinder side assembly parts 160 are attached to fuselage cylinder (as illustrated with 60 in figure 3).Similarly, floor side assembly parts 180 comprise and/or limit floor side holding structure 184, and this floor side holding structure is configured to operationally floor side assembly parts 180 are attached to floor grid (as illustrated with 80 in figure 3).
Cylinder side assembly parts 160 comprise further and/or limit alignment pin recess 120.Alignment pin recess 120 can be configured to receive the alignment pin 130 (such as rotator bolt) comprising and/or limit alignment surface 132.In the diagram, alignment pin 130 is depicted as and is separated (dotted line) with cylinder side assembly parts 160 and assembles two kinds of situations of (solid line) with cylinder side assembly parts 160.
Floor side assembly parts 180 comprise further and/or limit assembly alignment recess 110.As here discussed in more detail, assembly alignment recess 110 can size be formed as receiving alignment pin 130 and/or its alignment surface 132.In addition, and as also here discussed in more detail, assembly alignment recess 110 can allow alignment pin 130 and/or its alignment surface 132 translation wherein and can be shaped as preferably the cylinder side attachment hole 162 of cylinder side assembly parts 160 to be aimed at the floor side attachment hole 182 of floor side assembly parts 180.
Fig. 5-6 is the partial views according to autoregistration assembly 100 of the present disclosure.The autoregistration load module of Fig. 5-6 can be included in the autoregistration load module 100 of Fig. 1-4 and/or can be this autoregistration load module.Autoregistration load module 100 comprises floor side assembly parts 180 and cylinder side assembly parts 160.Cylinder side assembly parts 160 comprise and/or limit the alignment pin recess 120 with the alignment pin 130 be received in wherein.Alignment pin 130 comprises and/or limits alignment surface 132.Floor side assembly parts 180 comprise and/or limit assembly alignment recess 110, and alignment pin 130 extends through assembly alignment recess 110.In figures 5-6, cylinder side assembly parts 160 are positioned at floor side assembly parts 180 below and visible by means of only assembly alignment recess 110.
Assembly alignment recess 110 comprises and/or limits first area 112, second area 114 and the transitional region between first area 112 and second area 114 116.First area 112 size is formed as allowing alignment pin 130 and/or alignment surface 132 wherein on the direction being parallel to first direction 190 and translation on the direction being parallel to second direction 192.Second area 114 size is formed as allowing alignment pin 130 and/or alignment surface 132 translation on the direction being parallel to first direction 190 wherein, but restriction and/or in addition restriction alignment pin 130 and/or alignment surface 132 translation on the direction being parallel to second direction 192.
In operation, and as shown in fig. 5, and together with cylinder side assembly parts 160 and floor side assembly parts 180 can be placed down in first orientation 102 at first, this first orientation also can be called the first relative azimuth 102 in this article.First orientation 102 times, alignment pin 130 and/or its alignment surface 132 can be positioned in the first area 112 of assembly alignment recess 110.In addition, the cylinder side attachment hole 162 of cylinder side assembly parts 160 can not be aimed at the floor side attachment hole 182 of floor side assembly parts 180.
Subsequently, and as shown in fig. 6, and cylinder side assembly parts 160 and floor side assembly parts 180 can relative to each other move to second orientation 104, and this second orientation also can be called the second relative azimuth 104 in this article.Second orientation 104 times, alignment pin 130 and/or its alignment surface 132 can be positioned in the second area 114 of assembly alignment recess 110.In addition, the cylinder side attachment hole 162 of cylinder side assembly parts 160 can be aimed at the floor side attachment hole 182 of floor side assembly parts 180, be aimed at least in part and/or substantially aim at.
As illustrated in figures 5-6, transitional region 116 can be shaped as and preferably alignment pin 130 and/or its alignment surface 132 guided to second area 114 from first area 112.As illustrative non-exclusive example, and after autoregistration load module 100 is placed in first orientation 102 (as shown in fig. 5), floor side assembly parts 180 (and/or applying force to the floor grid 80 that can be attached to these floor side assembly parts) can be applied force to make alignment pin 130 from first area 112 towards second area 114 (as shown in fig. 6) propelling and/or to enter to this second area.In figures 5-6, this can be included in directed force on first direction 190.
As also illustrated in figures 5-6, can comprise cylinder side assembly parts 160 and floor side assembly parts 180 on the direction being parallel to first direction 190 and relative to each other translation on the direction being parallel to second direction 192 from the conversion of first orientation 102 to second orientation 104.As here discussed in more detail, in the scope of the present disclosure, the floor grid 80 being operationally attached to floor side assembly parts 180 can be at least substantially rigid on the direction being parallel to second direction 192, but can be relatively more flexible on the direction being parallel to first direction 190.Therefore, cylinder side assembly parts 160 and the translation of floor side assembly parts 180 relative to each other on the direction being parallel to first direction 190 can comprise the distortion of floor grid 80 on the direction being parallel to first direction 190.
In the scope of the present disclosure, operationally can be attached to a fuselage of side assembly parts 160 60 can be at least substantially rigid on the direction being parallel to first direction 190, but can be relatively more flexible on the direction being parallel to second direction 192.Therefore, cylinder side assembly parts 160 and the translation of floor side assembly parts 180 relative to each other on the direction being parallel to second direction 192 can comprise the distortion of fuselage cylinder 60 on the direction being parallel to second direction 192.
Assembly alignment recess 110 and/or first area 112, second area 114 and/or its transitional region 116 can be defined as any suitable shape.As illustrative non-exclusive example, first area 112 can be defined as (substantially) trapezoidal shape, the shape of (substantially) isosceles trapezoid, and/or the trapezoidal shape comprising and/or limit two (substantially) fillets.As illustrative non-exclusive example, second area 114 can limit the slit extended from first area 112.As another illustrative non-exclusive example, transitional region 116 can provide from (substantially) pulsation-free of first area 112 to second area 114, gradually and/or the transition of tilting (sloped).
As illustrated in figures 5-6, alignment pin 130 and/or its alignment surface can be defined as circular or at least almost circular cross sectional shape.When alignment pin 130 has circular cross sectional shape and second area 114 is slits, the width of slit can be greater than the diameter of alignment pin 130.The width of slit can also divide in rate (thresholdfraction) in the threshold value of the diameter of alignment pin 130.The illustrative non-exclusive example of threshold value point rate comprises such threshold value point rate, is namely less than 1% of the diameter of alignment pin 130, is less than 2%, is less than 3%, is less than 4%, is less than 5%, is less than 6%, is less than 7%, is less than 8%, is less than 9% or be less than 10%.
Fig. 7 is the diagram of circuit according to method 300 of the present disclosure describing assembling body.In the figure 7, some steps shown in dotted line frame represent that these steps can be optional versions (version, modification) that is optional or that can correspond to according to method 300 of the present disclosure.That is, do not really want rooting and all comprise the step shown in solid box according to all methods 300 of the present disclosure.As what be to be understood that according to discussion herein, method shown in Figure 7 and step are nonrestrictive, and additive method and step are also in the scope of the present disclosure, comprise the method for the quantity had greater or less than shown step.
Method 300 can comprise in step 305 operationally support floor grid and/or operationally support fuselage cylinder in the step 310.Method 300 comprises: in step 315 relative to fuselage cylinder translation floor grid; Operationally multiple alignment pin recess is aimed at multiple assembly alignment recess in step 320; In step 325 multiple alignment pin is positioned in multiple alignment pin recess; And in a step 330 floor grid is reduced relative to fuselage cylinder.Method 300 may further include: be positioned in body by multiple expansion pin in step 335; Multiple expansion pin is made to expand in step 340; Multiple floor side assembly parts are clamped to multiple corresponding side assembly parts in step 345; And/or in step 350 multiple expansion pin is removed from body.Method 300 is included in step 355 multiple fastener to be arranged in body and can to comprise further removes multiple alignment pin in step 360.
Operationally support floor grid can comprise and utilizes floor grid translation structure (the floor grid translation structure 30 of such as Fig. 2) operationally support floor grid in step 305.In addition or alternatively, operationally support to comprise in step 305 and utilize floor grid support fixture (the floor grid support fixture 34 of such as Fig. 2) operationally support floor grid.Operationally support fuselage cylinder in the step 310 can comprise and utilize fuselage cylinder supporting construction (the fuselage cylinder supporting construction 40 of such as Fig. 2) operationally to support fuselage cylinder.
Translation can be comprised relative to fuselage cylinder translation floor grid in step 315 to become operationally floor grid to be positioned in fuselage cylinder.Floor grid operationally can be attached to multiple floor side assembly parts, and fuselage cylinder operationally can be attached to multiple side assembly parts.Multiple floor side assembly parts can limit multiple floor side attachment hole, and multiple side assembly parts can limit multiple side attachment hole.Autoregistration load module can be formed, the autoregistration load module 100 of such as Fig. 1-6 together with each in the cylinder side assembly parts of the correspondence in multiple side assembly parts in multiple floor side assembly parts.
Operationally multiple alignment pin recess is aimed at multiple assembly alignment recess to comprise in step 320 and operationally aim to allow to position in step 325.Multiple alignment pin recess can be limited by the one in multiple floor side assembly parts and multiple side assembly parts and/or is formed in the one in multiple floor side assembly parts and multiple side assembly parts.Multiple assembly alignment recess can be limited by the another one in multiple floor side assembly parts and multiple side assembly parts and/or is formed in the another one in multiple floor side assembly parts and multiple side assembly parts.In the scope of the present disclosure, operationally aim at can be included in fuselage cylinder in step 320 and reduce floor grid, operationally corresponding in each and multiple assembly alignment recess in multiple alignment pin recess is aimed at.
Floor grid can limit the passenger surface with surface normal direction, and operationally aims to comprise in step 320 and floor grid is parallel on the direction in surface normal direction (at least basic) be out of shape.Operationally aligning in step 320 can also comprise makes fuselage cylinder be out of shape on (at least basic) direction perpendicular to surface normal direction.Make floor grid be out of shape can (at least basic) with fuselage cylinder is out of shape carry out simultaneously.
Multiple alignment pin is positioned in multiple alignment pin recess to comprise in step 325 and locates multiple alignment pin in any suitable manner.As illustrative non-exclusive example, location in step 325 can comprise multiple alignment pin bolt and/or be screwed in multiple alignment pin recess.As illustrative non-exclusive example, location in step 325 can also comprise to be put into multiple alignment pin, insert and/or is pressed into multiple alignment pin recess.
Multiple alignment pin can limit multiple corresponding alignment surface, and location in step 325 can also comprise and makes multiple alignment pin (and/or its multiple alignment surface) extend through corresponding assembly alignment recess.Therefore, after location in step 325, each in multiple alignment pin can extend and by corresponding assembly alignment recess in corresponding alignment pin recess.
Reduce floor grid relative to fuselage cylinder in a step 330 and can comprise reduction floor grid to make multiple side assembly parts and the relative to each other translation of multiple floor side assembly parts.This can comprise the translation from first orientation (wherein multiple floor side attachment hole do not aim at multiple side attachment hole) to second orientation (wherein multiple floor side attachment hole each aim at the corresponding cylinder side attachment hole in multiple side attachment hole at least in part).As here discussed in more detail, during assembly alignment recess can be shaped as reduction in a step 330, multiple floor side assembly parts and multiple side assembly parts being guided towards second orientation or preferably guiding.
In step 335 multiple expansion pin to be positioned in body and can to carry out before the installation after reduction in a step 330 and/or in step 355.Location in step 335 can comprise locates multiple expansion pin in any suitable manner.As illustrative non-exclusive example, location in step 335 can comprise make in multiple expansion pin each and extend through the floor side attachment hole selected in multiple floor side attachment hole and the cylinder side attachment hole by the correspondence in multiple side attachment hole.
Expand after the location making multiple expansion pin expand in step 340 can to comprise in step 335.As here discussed in more detail, before expansion in step 340, each in floor side attachment hole and corresponding cylinder side attachment hole can partly, but aim at by halves.Part is aimed at can be enough to allow location in step 335 but be not enough to allow the installation in step 355.Consider this point, expansion in step 340 can comprise such as makes multiple expansion pin expand by the external diameter increasing expansion pin, each with the corresponding cylinder side attachment hole in multiple floor side attachment hole to be aimed at, thus allows the installation in step 355.
Multiple floor side assembly parts are clamped to multiple corresponding side assembly parts in step 345 can comprise clamping and limit relative motion between multiple floor side assembly parts and multiple side assembly parts with (at least basic).In addition or alternatively, the clamping in step 345 can comprise clamping to keep the aligning of each with the corresponding cylinder side attachment hole in multiple floor side attachment hole.
In step 350 multiple expansion pin is removed to comprise from body and remove multiple expansion pin to allow the installation step 355.This can comprise from selected floor side attachment hole and to remove multiple expansion pin from the cylinder side attachment hole of correspondence each.Removing in step 350 can after the clamping in step 345.Therefore, in step 350 remove can be included in keep the aligning between each with the corresponding cylinder side attachment hole in multiple floor side attachment hole via the clamping in step 345 while remove multiple expansion pin.
In step 355, multiple fastener is arranged in body and can comprises that to make in multiple fastener each and extend through selected in multiple floor side attachment hole one and by the correspondence in multiple side attachment hole one.Installation in step 355 can also comprise fastening multiple fastener.When being included in the clamping in step 345 when method 300, multiple floor side assembly parts unclamp with multiple corresponding side assembly parts after may further include the installation in step 355 by method 300.When method 300 comprises removing in step 350, after the installation in step 355 can be removed in step 350.
Remove multiple alignment pin in step 360 can comprise and remove multiple alignment pin in any suitable manner.As illustrative non-exclusive example, in step 360 remove to comprise removes multiple alignment pin from multiple alignment pin recess.As illustrative non-exclusive example, in step 360 remove to comprise removes multiple alignment pin from body.
The illustrative non-exclusive example according to subject matter of the present disclosure is described in the paragraph enumerated below:
A1. an autoregistration load module, be configured to aim at and be operationally attached floor grid and the fuselage cylinder of aircraft, described assembly comprises:
Cylinder side assembly parts, be configured to operationally be attached to described fuselage cylinder, wherein said cylinder side assembly parts comprise multiple side attachment hole;
Floor side assembly parts, be configured to operationally be attached to described floor grid and be attached to described cylinder side assembly parts, wherein said floor side assembly parts comprise multiple floor side attachment hole, and further, wherein, each in described multiple floor side attachment hole is configured to operationally aim to corresponding in described multiple side attachment hole;
Alignment pin recess; And
Assembly alignment recess;
Wherein:
I () described alignment pin recess is formed in the one in described cylinder side assembly parts and described floor side assembly parts, and be configured to receive the alignment pin comprising alignment surface;
(ii) described assembly alignment recess is formed in the another one in described cylinder side assembly parts and described floor side assembly parts;
(iii) described alignment surface is stretched by described assembly alignment recess at described alignment pin by described alignment pin recess receive time delay; And
(iv) described assembly alignment recess size is formed as allowing the translation wherein of described alignment surface, thus allow translation in described cylinder side assembly parts and multiple relative azimuths of described floor side assembly parts relative to each other between first orientation and second orientation, wherein in first orientation, described multiple floor side attachment hole is not aimed at described multiple side attachment hole, in second orientation, described multiple floor side attachment hole is aimed at described multiple side attachment hole.
A2. the assembly according to paragraph A1, wherein, described assembly alignment recess comprises:
(i) first area, size is formed as allowing described alignment surface wherein on the direction being parallel to first direction and translation on the direction being parallel to second direction, and described second direction is perpendicular to described first direction; And
(ii) second area, size is formed as allowing the translation on the direction being parallel to described first direction wherein of described alignment surface, but limits the translation of described alignment surface on the direction being parallel to described second direction.
A3. the assembly according to paragraph A2, wherein, described assembly alignment recess comprises the transitional region between described first area and described second area further.
A4. the assembly according to paragraph A3, wherein, described transitional region is configured as and preferably described alignment surface is guided to described second area from described first area.
A5. the assembly according to any a section in paragraph A2-A4, wherein, described first orientation corresponds to described alignment surface and is positioned in described first area.
A6. the assembly according to any a section in paragraph A2-A5, wherein, described second orientation corresponds to described alignment surface and is positioned in described second area.
A7. the assembly according to any a section in paragraph A2-A6, wherein, described first area comprises trapezoidal shape, and comprises isosceles-trapezium-shaped alternatively.
A8. the assembly according to paragraph A7, wherein, described trapezoidal shape comprises two fillets.
A9. the assembly according to any a section in paragraph A2-A8, wherein, described second area comprises the slit extended from described first area.
A10. the assembly according to paragraph A9, wherein, described alignment surface comprises the circular section shape with diameter, the width of wherein said slit be greater than described alignment surface diameter and in the threshold value point rate of the diameter of described alignment surface.
A11. the assembly according to paragraph A10, wherein, described threshold value point rate be less than the diameter of described alignment surface 1%, be less than 2%, be less than 3%, be less than 4%, be less than 5%, be less than 6%, be less than 7%, be less than 8%, be less than 9% or be less than 10%.
A12. the assembly according to any a section in paragraph A1-A11, wherein, described alignment pin recess is formed in the assembly parts of described cylinder side, and further, wherein, described assembly alignment recess is formed in described floor side assembly parts.
A13. the assembly according to any a section in paragraph A1-A12, wherein, described multiple side attachment hole comprise at least two cylinder side attachment hole, and just in time two cylinder side attachment hole alternatively.
A14. the assembly according to any a section in paragraph A1-A13, wherein, described multiple floor side attachment hole comprises at least two floor side attachment hole, and just in time two floor side attachment hole alternatively.
A15. the assembly according to any a section in paragraph A1-A14, wherein, described cylinder side assembly parts comprise a side holding structure, and described cylinder side holding structure is configured to operationally described cylinder side assembly parts are attached to described fuselage cylinder.
A16. the assembly according to any a section in paragraph A1-A15, wherein, described floor side assembly parts comprise floor side holding structure, and described floor side holding structure is configured to operationally described floor side assembly parts are attached to described floor grid.
A17. the assembly according to any a section in paragraph A1-A16, wherein, described alignment pin recess comprises hole, cylindrical hole alternatively, size is formed as the cylindrical hole of the threaded portion receiving described alignment pin alternatively, and further alternatively size be formed as the cylindrical hole with shallow embedding head bore receiving the described threaded portion of described alignment pin and a part for described alignment surface.
A18. the assembly according to any a section in paragraph A1-A17, wherein, described assembly comprises described alignment pin, and further, wherein, described alignment pin is received in described alignment pin recess.
A19. the assembly according to paragraph A18, wherein, described alignment pin extends through described assembly alignment recess.
A20. the assembly according to any a section in paragraph A18-A19, wherein, described cylinder side assembly parts and described floor side assembly parts are under first orientation.
A21. the assembly according to any a section in paragraph A18-A20, wherein, described cylinder side assembly parts and described floor side assembly parts are under second orientation.
A22. the assembly according to any a section in paragraph A18-A21, wherein, described alignment pin comprises and is rotator bolt alternatively.
A23. the assembly according to any a section in paragraph A1-A22, wherein, described assembly comprises expansion pin, and described expansion pin is configured to operationally the floor side attachment hole selected by described multiple floor side attachment hole be aimed at the corresponding cylinder side attachment hole in described multiple side attachment hole.
A24. the assembly according to paragraph A23, wherein, described expansion pin is configured to change having between the retracted configuration of contracted diameter and the expansion form with swell diameter, operationally selected floor side attachment hole to be aimed at described corresponding cylinder side attachment hole, wherein said contracted diameter is less than described swell diameter.
A25. the assembly according to any a section in paragraph A1-A24, wherein, described assembly comprises multiple fastener further, each cylinder side attachment hole extending through the selected floor side attachment hole in described multiple floor side attachment hole and extend through the correspondence in described multiple side attachment hole in wherein said multiple fastener, to be operationally attached to described floor side assembly parts by described cylinder side assembly parts.
B1. a body, comprising:
Fuselage cylinder;
Floor grid; And
Autoregistration load module, is operationally attached to described floor grid by described fuselage cylinder.
B2. the body according to paragraph B1, wherein, described autoregistration load module comprises the autoregistration load module according to any a section in paragraph A1-A25.
B3. the body according to paragraph B2, wherein, described cylinder side assembly parts are operationally attached, and are directly attached to described fuselage cylinder alternatively.
B4. the body according to any a section in paragraph B2-B3, wherein, described floor side assembly parts are operationally attached, and are directly attached to described floor grid alternatively.
B5. an aircraft, comprising:
Body according to any a section in paragraph B1-B4.
C1. a body package system, be configured to floor grid aimed at and be operationally attached to fuselage cylinder, described system comprises:
Floor grid translation structure, is configured to support described floor grid and operationally locates described floor grid relative to described fuselage cylinder;
Fuselage cylinder supporting construction, is configured to operationally support described fuselage cylinder; And
Body according to any a section in paragraph B1-B4.
C2. the system according to paragraph C1, wherein, described floor grid translation structure comprises gauntry crane, and described gauntry crane is configured to operationally floor grid described in translation, operationally to locate described floor grid relative to described fuselage cylinder.
C3. the system according to any a section in paragraph C1-C2, wherein, described floor grid translation structure comprises floor grid support fixture, and described floor grid support fixture is configured to support described floor grid.
D1. assemble a method for body, described method comprises:
Relative to fuselage cylinder translation floor grid, described floor grid is operationally positioned in described fuselage cylinder, wherein said floor grid is operationally attached to the multiple floor side assembly parts comprising multiple floor side attachment hole, and further, wherein, described fuselage cylinder is operationally attached to the multiple side assembly parts comprising multiple side attachment hole;
Multiple alignment pin recess is operationally aimed at corresponding multiple assembly alignment recesses, wherein said multiple alignment pin recess is formed in the one in described multiple floor side assembly parts and described multiple side assembly parts, and further, wherein, described multiple assembly alignment recess is formed in the another one in described multiple floor side assembly parts and described multiple side assembly parts;
Multiple alignment pin is positioned in described multiple alignment pin recess, wherein said multiple alignment pin comprises multiple alignment surface, and further, wherein, this location comprises and makes described multiple alignment surface extend through corresponding assembly alignment recess in described multiple assembly alignment recess;
Described floor grid is reduced relative to described fuselage cylinder, to make described multiple side assembly parts and described multiple floor side assembly parts relative to each other move to second orientation from first orientation, in described first orientation, described multiple floor side attachment hole is not aimed at described multiple side attachment hole, in second orientation, each in described multiple floor side attachment hole aims at the corresponding cylinder side attachment hole in described multiple side attachment hole at least in part, wherein said multiple assembly alignment recess is configured as and described multiple floor side assembly parts and described multiple side assembly parts is guided towards described second orientation during this reduction, and
One selected by extending through in described multiple side attachment hole by make in multiple fastener each and by one of the correspondence in described multiple floor side attachment hole, described multiple fastener is arranged in described body.
D2. the method according to paragraph D1, wherein, the step of operationally aiming at is included in described fuselage cylinder and reduces described floor grid, operationally to be aimed at corresponding described multiple assembly alignment recesses by described multiple alignment pin recess.
D3. the method according to any a section in paragraph D1-D2, wherein, before the step of translation, described method comprises further and utilizes floor grid translation structure operationally to support described floor grid.
D4. the method according to any a section in paragraph D1-D3, wherein, before the step of translation, described method comprises further and utilizes fuselage cylinder supporting construction operationally to support described fuselage cylinder.
D5. the method according to any a section in paragraph D1-D4, wherein, after the step of installing, described method comprises further removes described multiple alignment pin from described multiple alignment pin recess.
D6. the method according to any a section in paragraph D1-D5, wherein, described body comprises the body according to any a section in paragraph B1-B4.
D7. the method according to any a section in paragraph D1-D6, wherein, described method comprises the system of use according to any a section in paragraph C1-C3 further and performs described method.
D8. the method according to any a section in paragraph D1-D7, wherein, after reducing the step of described floor grid relative to described fuselage cylinder and before the step of installing, described method comprises further and is positioned in described body by multiple expansion pin, and each in wherein said multiple expansion pin extends through selected floor side attachment hole and extend through corresponding cylinder side attachment hole.
D9. the method according to paragraph D8, wherein, described method comprises further makes described multiple expansion pin expand, to make each with the corresponding described cylinder side attachment hole in described multiple floor side attachment hole aim at.
D10. the method according to any a section in paragraph D8-D9, wherein, described method comprises each cylinder side assembly parts being clamped to correspondence in described multiple floor side assembly parts further, to limit the relative motion between it.
D11. the method according to paragraph D10, wherein, after the step of clamping, described method comprises further from selected floor side attachment hole and to remove described multiple expansion pin from the described cylinder side attachment hole of correspondence each.
D12. the method according to paragraph D11, wherein, the step of installation is carried out after the step removing expansion pin.
D13. the method according to any a section in paragraph D1-D12, wherein, described floor grid comprises the passenger surface with way bill facial plane, this way bill facial plane has surface normal direction, and further, wherein, the step of operationally aiming at comprises makes described floor grid be out of shape on the direction being parallel to described surface normal direction and make described fuselage cylinder be out of shape on the direction perpendicular to described surface normal direction simultaneously.
As used herein, term " selection " and " optionally ", the action of the one or more parts of modification device or characteristic, movement, structure or other movable time, mean that specific action, movement, structure or other activities are an aspect of user operation equipment or the direct or indirect result of one or more parts.
As used herein, term " adaptation " and " structure " mean that element, parts or other themes are designed and/or are intended to carry out given function.Therefore, term " adaptation " and " structure " should not be interpreted as meaning point element, parts or other themes only " can " perform given function, but for the object of n-back test, select particularly, create, realize, utilize, programme and/or design element, parts and/or other themes.Same within the scope of present disclosure, element, parts and/or themes of being set fourth as other statements being suitable for performing specific function can be described as extraly or being alternatively configured to perform that function, vice versa.Similarly, be set fourth as and be configured to perform the theme of specific function and can be described as extraly or alternatively and operationally perform that function.
The step of the element of various disclosed equipment and in this article disclosed method is non-essential is all devices according to present disclosure and method, and present disclosure comprise all newly and the sub-portfolio of non-obvious combination and in this article disclosed various element and step.In addition, disclosed one or more various element and step can limit the independent invention theme being separated with whole disclosed equipment or method and separating in this article.Therefore, do not require this kind of subject matter and clear and definite disclosed concrete equipment is relevant with method in this article, and the function of this kind of subject matter can be found in this article in clear and definite disclosed equipment and/or method.
Claims (15)
1. an autoregistration load module, be configured to aim at and be operatively attached the floor grid (80) of aircraft and fuselage cylinder (60), described autoregistration load module comprises:
Cylinder side assembly parts (160), be configured to operatively be attached to described fuselage cylinder, wherein said cylinder side assembly parts comprise multiple side attachment hole (162);
Floor side assembly parts (180), be configured to operatively be attached to described floor grid and be attached to described cylinder side assembly parts, wherein said floor side assembly parts comprise multiple floor side attachment hole (182), and further, wherein, each floor side attachment hole in described multiple floor side attachment hole is configured to a cylinder side attachment hole corresponding to described multiple side attachment hole and operatively aims at;
Alignment pin recess (120);
Assembly alignment recess (110); And
Alignment pin (130), comprises alignment surface (132);
Wherein:
I () described alignment pin recess is formed in the one in described cylinder side assembly parts and described floor side assembly parts, and be configured to receive described alignment pin;
(ii) described assembly alignment recess is formed in the another one in described cylinder side assembly parts and described floor side assembly parts;
(iii) described alignment pin is received in described alignment pin recess, and described alignment surface extends through described assembly alignment recess; And
(iv) described assembly alignment recess size is formed as allowing the translation wherein of described alignment surface, thus allow translation in described cylinder side assembly parts and multiple relative azimuths of described floor side assembly parts relative to each other between first orientation (102) and second orientation (104), wherein in described first orientation, described multiple floor side attachment hole is not aimed at described multiple side attachment hole, in described second orientation, described multiple floor side attachment hole is aimed at described multiple side attachment hole.
2. assembly according to claim 1 (100), wherein, described assembly alignment recess (110) comprising:
(i) first area (112), size is formed as allowing described alignment surface (132) wherein on the direction being parallel to first direction (190) and translation on the direction being parallel to second direction (192), and described second direction is perpendicular to described first direction; And
(ii) second area (114), size is formed as allowing the translation on the direction being parallel to described first direction wherein of described alignment surface, but limits the translation of described alignment surface on the direction being parallel to described second direction.
3. assembly according to claim 2 (100), wherein, described assembly alignment recess (110) comprises the transitional region (116) be positioned between described first area (112) and described second area (114) further, and wherein said transitional region is configured as and preferably described alignment surface (132) is guided to described second area from described first area; And wherein said first orientation (102) is positioned in described first area corresponding to described alignment surface, and further, wherein, described second orientation (104) is positioned in described second area corresponding to described alignment surface.
4. the assembly (100) according to any one of claim 2 to 3, wherein, described first area (112) comprise trapezoidal shape; And wherein said second area (114) comprises the slit extended from described first area.
5. the assembly (100) according to any one in aforementioned claim, wherein, described cylinder side assembly parts (160) comprises cylinder side holding structure (164) being configured to described cylinder side assembly parts are operatively attached to described fuselage cylinder (60), and further, wherein, described floor side assembly parts (180) comprise the floor side holding structure (184) being configured to described floor side assembly parts are operatively attached to described floor grid (80).
6. the assembly (100) according to any one in aforementioned claim, wherein, described alignment pin (130) is rotator bolt.
7. the assembly (100) according to any one in aforementioned claim, wherein, described autoregistration load module comprises expansion pin (140), the cylinder side attachment hole that described expansion pin is configured to the floor side attachment hole selected in described multiple floor side attachment hole (182) is corresponding with described multiple side attachment hole (162) is operatively aimed at, and further, wherein, described expansion pin is configured to change having between the retracted configuration of contracted diameter and the expansion form with swell diameter, selected floor side attachment hole is operatively aimed at corresponding cylinder side attachment hole, wherein said contracted diameter is less than described swell diameter.
8. the assembly (100) according to any one in aforementioned claim, wherein, described autoregistration load module comprises multiple fastener further, the cylinder side attachment hole that each fastener in wherein said multiple fastener is corresponding in extending through the floor side attachment hole selected in described multiple floor side attachment hole (182) and extending through described multiple side attachment hole (162), to be operatively attached to described floor side assembly parts (180) by described cylinder side assembly parts (160).
9. a body (50), comprising:
Autoregistration load module (100) according to any one in aforementioned claim;
Described fuselage cylinder (60); And
Described floor grid (80), wherein said cylinder side assembly parts (160) is operatively attached to described fuselage cylinder, and further, wherein, described floor side assembly parts (180) are operatively attached to described floor grid.
10. a body package system (20), be configured to floor grid (80) aimed at and be operatively attached to fuselage cylinder (60), described body package system comprises:
Floor grid translation structure (30), is configured to support described floor grid and operatively locates described floor grid relative to described fuselage cylinder;
Fuselage cylinder supporting construction (40), is configured to operatively support described fuselage cylinder; And
Body according to claim 9 (50).
The method of 11. 1 kinds of assemblings body (50), described method comprises:
Relative to fuselage cylinder (60) translation floor grid (80), described floor grid is operatively positioned in described fuselage cylinder, wherein said floor grid is operatively attached to the multiple floor side assembly parts (180) comprising multiple floor side attachment hole (182), and further, wherein, described fuselage cylinder is operatively attached to the multiple side assembly parts (160) comprising multiple side attachment hole (162);
Multiple alignment pin recess (120) is operatively aimed at corresponding multiple assembly alignment recesses (110), wherein said multiple alignment pin recess is formed in the one in described multiple floor side assembly parts and described multiple side assembly parts, and further, wherein, described multiple assembly alignment recess is formed in the another one in described multiple floor side assembly parts and described multiple side assembly parts;
Multiple alignment pin (130) is positioned in described multiple alignment pin recess, wherein said multiple alignment pin comprises multiple alignment surface (132), and further, wherein, the step of location comprises and makes described multiple alignment surface extend through corresponding assembly alignment recess in described multiple assembly alignment recess;
Described floor grid is reduced relative to described fuselage cylinder, to make described multiple side assembly parts and described multiple floor side assembly parts relative to each other move to second orientation (104) from first orientation (102), wherein in described first orientation, described multiple floor side attachment hole is not aimed at described multiple side attachment hole, in described second orientation, corresponding with the described multiple side attachment hole at least in part cylinder side attachment hole of each floor side attachment hole in described multiple floor side attachment hole is aimed at, wherein said multiple assembly alignment recess is configured as and guides described multiple floor side assembly parts and described multiple side assembly parts towards described second orientation during the step reduced, and
By making each fastener in multiple fastener extend through a cylinder side attachment hole selected in described multiple side attachment hole and a floor side attachment hole by correspondence in described multiple floor side attachment hole, and described multiple fastener is arranged in described body.
12. methods according to claim 11, wherein, after the step of installing, described method comprises further removes described multiple alignment pin (130) from described multiple alignment pin recess (120).
13. according to claim 11 to the method described in any one in 12, wherein, after reducing the step of described floor grid (80) relative to described fuselage cylinder (60) and before the step of installing, described method comprises further and is positioned in described body (50) by multiple expansion pin (140), and each expansion pin in wherein said multiple expansion pin extends through selected floor side attachment hole (182) and extends through corresponding cylinder side attachment hole (162).
14. methods according to claim 13, wherein, described method comprises further:
Described multiple expansion pin (140) is expanded, to make each floor side attachment hole in described multiple floor side attachment hole (182) aim at corresponding cylinder side attachment hole (162); And
Each floor side assembly parts in described multiple floor side assembly parts (180) are clamped to corresponding cylinder side assembly parts (160), to limit the relative motion between it, wherein, after the step of clamping, described method comprises further from selected floor side attachment hole and removes each expansion pin described multiple expansion pin from the cylinder side attachment hole of correspondence.
15. according to claim 11 to the method described in any one in 14, wherein, described floor grid (80) comprises the passenger surface (82) with way bill facial plane, described way bill facial plane has surface normal direction (84), and further, wherein, the step of operatively aiming at comprises makes described floor grid be out of shape on the direction being basically parallel to described surface normal direction, and makes described fuselage cylinder (60) be out of shape on the direction being basically perpendicular to described surface normal direction simultaneously.
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| US61/889,186 | 2013-10-10 | ||
| US14/261,217 US9199715B2 (en) | 2013-10-10 | 2014-04-24 | Self-aligning fitting assemblies and systems and methods including the same |
| US14/261,217 | 2014-04-24 | ||
| PCT/US2014/046968 WO2015053836A1 (en) | 2013-10-10 | 2014-07-17 | Self-aligning fitting assemblies and systems and methods including the same |
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| CN105555660B CN105555660B (en) | 2018-08-10 |
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| CN201480051396.0A Active CN105555660B (en) | 2013-10-10 | 2014-07-17 | Autoregistration assembling assembly and the system and method for including autoregistration assembling assembly |
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| EP (1) | EP3055202B1 (en) |
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- 2014-07-17 EP EP14748044.6A patent/EP3055202B1/en active Active
- 2014-07-17 JP JP2016518154A patent/JP6359094B2/en active Active
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| CN104890856A (en) * | 2014-03-07 | 2015-09-09 | 空中客车运营简化股份公司 | Device for relative positioning of two aircraft parts, such as a crossbeam and a fuselage frame |
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| CN107364565B (en) * | 2016-05-11 | 2022-11-04 | 波音公司 | Method for optimizing alignment between components using predictive shimming |
| CN112534169A (en) * | 2018-07-17 | 2021-03-19 | 肯发系统有限公司 | Mounting structure of flow substrate |
Also Published As
| Publication number | Publication date |
|---|---|
| EP3055202A1 (en) | 2016-08-17 |
| WO2015053836A1 (en) | 2015-04-16 |
| JP2016536185A (en) | 2016-11-24 |
| ES2727708T3 (en) | 2019-10-18 |
| CN105555660B (en) | 2018-08-10 |
| EP3055202B1 (en) | 2019-03-06 |
| US20150102170A1 (en) | 2015-04-16 |
| JP6359094B2 (en) | 2018-07-18 |
| US9199715B2 (en) | 2015-12-01 |
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